EP3288831B1 - Stackable satellites and method of stacking same - Google Patents

Stackable satellites and method of stacking same Download PDF

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Publication number
EP3288831B1
EP3288831B1 EP16787044.3A EP16787044A EP3288831B1 EP 3288831 B1 EP3288831 B1 EP 3288831B1 EP 16787044 A EP16787044 A EP 16787044A EP 3288831 B1 EP3288831 B1 EP 3288831B1
Authority
EP
European Patent Office
Prior art keywords
satellite
stackable
satellites
vertical
frame
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP16787044.3A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3288831A1 (en
EP3288831A4 (en
Inventor
Daniel W. FIELD
Armen ASKIJIAN
James Grossman
Alexander D. Smith
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
WorldVu Satellites Ltd
Original Assignee
WorldVu Satellites Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication date
Application filed by WorldVu Satellites Ltd filed Critical WorldVu Satellites Ltd
Publication of EP3288831A1 publication Critical patent/EP3288831A1/en
Publication of EP3288831A4 publication Critical patent/EP3288831A4/en
Application granted granted Critical
Publication of EP3288831B1 publication Critical patent/EP3288831B1/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641—Interstage or payload connectors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641—Interstage or payload connectors
    • B64G1/643—Interstage or payload connectors for arranging multiple satellites in a single launcher
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641—Interstage or payload connectors
    • B64G1/643—Interstage or payload connectors for arranging multiple satellites in a single launcher
    • B64G1/644—Interstage or payload connectors for arranging multiple satellites in a single launcher arranged for independent deployment

Definitions

  • the present invention is related to satellites, and in particular, satellite structure design for maximizing payload in a launch vehicle.
  • a satellite support system typically connects satellites to a launch vehicle through a specified interface plane and bolt pattern. Individual satellites can attach directly to such an interface. For launching multiple satellites such as a group of medium earth orbit (MEO) or low earth orbit (LEO) satellites, the support system typically uses a dispenser having a primary cylinder that is cantilevered off of the interface plane. Individual satellites can then be attached radially around the perimeter of the primary cylinder.
  • MEO medium earth orbit
  • LEO low earth orbit
  • EP 2662287 relates to a multiple space vehicle lunch system.
  • EP 1008516 relates to a satellite dispenser device.
  • US 5522569 relates to a satellite having a stackable configuration.
  • a stackable satellite comprising a frame and at least one vertical pillar attached to the frame.
  • the vertical pillar has an upper end and a lower end. The upper end is coupled to the lower end of the vertical pillar on the satellite above and the lower end is coupled to the upper end of the vertical pillar on the satellite below.
  • the vertical pillar receives substantially all of the vertical load of the attached stackable satellite and any upper stackable satellites. Use of such vertical pillars removes the need for a dispenser or substantially lightens the dispenser mass to allow substantially more satellites to be carried in a payload.
  • a method of preparing a payload containing a plurality of stackable satellites includes vertically positioning the stackable satellites over a base. Each stackable satellite having a frame and at least one vertical pillar attached to the frame. The satellites are stacked such that the lower end of the vertical pillar is coupled to an upper end of the vertical pillar on the satellite below and the upper end is coupled to the lower end of the vertical pillar of the satellite above. When stacked in this manner, the vertical pillar of the satellite receives substantially all of the vertical load of the satellite it is attached to and any satellites stacked above. The method further includes fastening the stacked satellites to the base of the launch vehicle by applying downward pressure through the vertical pillars of the stackable satellites.
  • the disclosure described herein is a novel satellite design and a method where multiple satellites are stacked in a launch vehicle without using a common heavy dispenser.
  • the satellites are stacked directly over each other through vertical pillars that carry substantially all of the launch vehicle loads.
  • the vertical pillars are designed to carry the main static and dynamic loads of the satellites above.
  • the pillar geometry is specifically designed for these loads to bypass the rest of the satellite structure and transmit directly from pillar to pillar until the bottom pillar carries the load into the launch vehicle.
  • only the vertical pillars are designed for very high strength and stiffness without requiring the same performance criteria from the rest of the satellite structure such as the frame.
  • these load paths can be made more effective by preloading them in compression by compressing the stack of satellites.
  • the preload resists tensile loads in the opposite direction so that the loads are not reversible and nonlinear gapping responses are reduced or eliminated.
  • each satellite in the stack would then separate from the launch vehicle individually.
  • FIG. 1 depicts a perspective view of a stackable satellite according to one aspect of the present invention.
  • a stackable satellite 50 includes a frame 52, vertical pillars 54 having a lower end 56 and upper end 58 and a plurality of panels 60 that support various satellite components such as antennas 90, fuel tank 92, propulsion systems, solar panels and the like.
  • the vertical pillars 54 and the panels 60 are typically attached to the satellite frame 52 with bolts.
  • stackable satellite 50 is shown with four vertical pillars 54, the principles disclosed herein can apply to any satellite with one or more pillars although three or more pillars are preferable.
  • FIG. 2 depicts a perspective view of a joint 66 that attaches a vertical pillar 54 to a frame 52 of the stackable satellite 50 of FIG. 1 .
  • the joint 66 such as a shear tie connects the vertical pillars 54 to an upper frame section 52a and lower frame section 52b of the satellite frame 52.
  • the shear tie 66 wraps around the vertical pillar 54 to uniformly spread the vertical load of the satellite 50 to the four pillars.
  • the shear tie 66 can be fastened to the frames 52a, 52b through a permanent mechanical fastener such as rivets 82 or bolts.
  • a permanent mechanical fastener such as rivets 82 or bolts.
  • four upper fasteners 82 fasten the vertical pillars 54 to the upper frame section 52a and four lower fasteners fasten the vertical pillars 54 to the lower frame section 52b.
  • four rivets 82 are used as upper fasteners and four additional rivets 82 are used as lower fasteners.
  • the portion of the pillar 54 that contacts the shear tie 66 can have a slight circumferential recess to receive the shear tie to prevent any vertical slippage of the satellite 50 from the pillars 54.
  • the vertical pillars are permanently attached to the respective satellite 50 and is designed to be a permanent part even when the satellite separates into its unique orbit.
  • the vertical pillars 54 need to support the weight of the satellite 50 they are attached to and any other satellites above it. Accordingly, they need to be made of very high strength material.
  • alloy or composite such as austenite nickel-chromium-based super alloys (e.g., Inconel available from Special Metals Corporation of New Hartford, NY) can be used.
  • the satellite frame 52 and the shear tie 66 only need to support the satellite's own mass. Accordingly, they can be made of relatively inexpensive materials such as aluminum, steel, synthetic fiber, glass fiber, carbon fiber material and the like.
  • the frame 52 includes carbon fiber material, which is relatively strong, stiff and light weight compared to metal such as aluminum.
  • the vertical pillars 54 are relatively expensive due to their structural integrity requirement of supporting the weight of multiple satellites, the pillars comprise only a very small portion of the payload.
  • the cost of the satellite frame 52 is relatively inexpensive and lightweight because they do not need to support the weight of any satellite 50 above its own frame. Consequently, substantial cost and weight savings over the conventional methods can be achieved.
  • FIG. 3A is a cross-sectional view of an upper end 56 of the vertical pillar 54 of one satellite 50 supporting a lower end 56 of the vertical pillar of a satellite immediately above it.
  • the upper end 58 has a conical recess that receives and supports a slightly convexly curved shape (protruding portion) such as a spherical protrusion of the lower end 56.
  • the conical recess of the upper end 58 provides vertical as well as lateral support of the satellite 50 above it.
  • FIG. 3B is an alternative embodiment of the upper and lower ends 56,58 of the vertical pillar 54.
  • the upper end 58 has a frusto-conical shape (protruding portion) that supports and mates with a complimentary frusto-conical recess of the lower end 56 to provide even more lateral support than those of FIG. 3A .
  • FIG. 4 is a cross-sectional side view of a plurality of stacked satellites using the stackable satellite of FIG. 1 .
  • all of the satellites 50 and vertical pillars 54 are identical to each other.
  • the satellites 50 are stacked on top of each other such that the only contact between the vertically stacked satellites is through the vertical pillars 54.
  • the upper ends 58 of a vertical pillar 48 of each stackable satellite 50 couples to and supports respective lower ends 56 of the vertical pillars of the satellite immediately above it. Since the only vertical contact between satellites 50 is through the vertical pillars, the pillars receive substantially all of the vertical load of the satellite they are attached to as well as all of the stackable satellites above it. In other words, the satellite frame 52 receives substantially none of the vertical load of any stacked satellite above it.
  • a satellite fastener 61 includes an upper lid 62, a lower lid 64, tension shaft 68, tension shaft brace 72 and upper shaft bolt 76.
  • the tension shaft 68 is positioned along the central axis of the launch vehicle to vertically compress the stack of satellites 50.
  • the tension shaft 68 has a lower end which is attached to the lower lid 64 and an upper end attached to the upper lid 62.
  • the lower lid 64 can be mounted directly onto an upper stage of the launch vehicle or indirectly mounted thereto through a payload adapter fitting (PAF) 65. If so, tension cables 70 secures attached to the lower lid 64 on one end and to the PAF 65 at the other end secures the lower lid to the launch vehicle.
  • PAF payload adapter fitting
  • the upper lid 62 has a central opening through which the bolt 76 is threaded.
  • the bolt 76 attaches the lid 62 to the tension shaft 68.
  • the lower lid 64 has a central opening through which a bolt (not shown) attaches the lid to the tension shaft 68.
  • the upper and lower lids 62,64 have a plurality of struts 78.
  • the tension shaft 68 does not need to support such weight. Accordingly, the tension shaft 68 could be made substantially lighter and thinner than was previously necessary.
  • the distal ends of the struts 78 for the upper lid 62 are shaped to mate with respective upper ends 58 of the pillars 54 of the uppermost satellites 50 to apply downward pressure through respective outer pillars and inner pillars to reduce or eliminate the likelihood of a lateral satellite movement during launch.
  • the distal ends of the struts 78 for the upper lid 62 are identical to the lower end 56 of the vertical pillars 54.
  • the distal ends of the struts 78 for the lower lid 64 are shaped to mate with respective lower ends 56 of the pillars 54 of the lowermost satellites 50.
  • the distal ends of the struts 78 for the lower lid 64 are identical to the upper end 58 of the vertical pillars 54.
  • the upper lid 62 and the bolt 76 are designed to be detached in orbit through known methods to allow the satellites 50 to be separated from the launch vehicle.
  • FIG. 5 is a perspective view of a plurality of stacked satellites using the stackable satellite of FIG. 1 according to another aspect of the present invention. For clarity, some parts of the satellite fastener 61are not shown in this figure. As shown, eight stackable satellites 50 are arranges horizontally around a central vertical axis and nine satellites are stacked vertically for each column of satellites for a total of 72 satellites that can be launched in a single payload.
  • the vertical pillars are designed to bypass the main static and dynamic loads of the satellites above. In this way, only the vertical pillars are designed for very high strength and stiffness without requiring the same performance criteria from the rest of the satellite structure.
  • the use of such vertical pillars either removes the need for a dispenser or substantially lightens the dispenser mass to allow substantially more satellites to be carried in a payload as illustrated in FIG. 5 , for example.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Radio Relay Systems (AREA)
  • Details Of Aerials (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Support Of Aerials (AREA)
EP16787044.3A 2015-04-30 2016-04-27 Stackable satellites and method of stacking same Active EP3288831B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US14/700,466 US9718566B2 (en) 2015-04-30 2015-04-30 Stackable satellites and method of stacking same
PCT/US2016/029509 WO2016176298A1 (en) 2015-04-30 2016-04-27 Stackable satellites and method of stacking same

Publications (3)

Publication Number Publication Date
EP3288831A1 EP3288831A1 (en) 2018-03-07
EP3288831A4 EP3288831A4 (en) 2018-09-05
EP3288831B1 true EP3288831B1 (en) 2020-06-24

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EP16787044.3A Active EP3288831B1 (en) 2015-04-30 2016-04-27 Stackable satellites and method of stacking same

Country Status (10)

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US (1) US9718566B2 (es)
EP (1) EP3288831B1 (es)
JP (1) JP6480013B2 (es)
KR (1) KR102133819B1 (es)
CN (1) CN107889482B (es)
CA (1) CA2983494C (es)
ES (1) ES2817008T3 (es)
IL (1) IL254804B (es)
SG (1) SG11201708248VA (es)
WO (1) WO2016176298A1 (es)

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Also Published As

Publication number Publication date
US20160318635A1 (en) 2016-11-03
CA2983494A1 (en) 2016-11-03
IL254804A0 (en) 2017-12-31
KR102133819B1 (ko) 2020-07-14
WO2016176298A1 (en) 2016-11-03
JP2018514441A (ja) 2018-06-07
IL254804B (en) 2018-08-30
CN107889482A (zh) 2018-04-06
CA2983494C (en) 2018-04-03
KR20170142187A (ko) 2017-12-27
EP3288831A1 (en) 2018-03-07
US9718566B2 (en) 2017-08-01
CN107889482B (zh) 2021-05-25
ES2817008T3 (es) 2021-04-06
JP6480013B2 (ja) 2019-03-06
SG11201708248VA (en) 2017-11-29
EP3288831A4 (en) 2018-09-05

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